中心锥体结构脉冲爆震火箭发动机初步实验

严宇; 范玮; 王可; 穆杨

中心锥体结构脉冲爆震火箭发动机初步实验

基金项目: 国家自然科学基金项目(50976094); 教育部博士点基金项目(20096102110022)

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出版历程
- 收稿日期: 2010-11-19
- 修回日期: 2011-02-22
- 刊出日期: 2011-11-28

Preliminary experimental investigation on pulse detonation rocket engine with central cone configuration

摘要

摘要: 为了改善采用液态燃料的脉冲爆震火箭发动机内部燃料的雾化以及燃料混合物的掺混状况,采用了一种中心锥体结构.该结构发动机不采用Shchelkin螺旋增爆装置,而采用中心锥体结构、二级供应方式.采用航空煤油为燃料、压缩氧气为氧化剂、压缩氮气为隔离气体,在该结构脉冲爆震火箭发动机上获得了充分发展的爆震波并且能够在多循环条件下稳定工作.实验结果表明,该结构可以大大缩短DDT(deflagration to detonation transition)距离,在实验条件下爆燃向爆震转变距离约为管径的5倍.较之同一管径采用Shchelkin螺旋增爆装置的脉冲爆震火箭发动机,该结构发动机的爆燃向爆震转变距离缩短了57.5%.
- 液态燃料 /
- 脉冲爆震火箭发动机 /
- 中心锥体 /
- 二级供应 /
- DDT(deflagration to detonation transition)距离
Abstract: In order to improve the atomization of liquid fuel and mixing of reactants inside the pulse detonation rocket engine using liquid fuel,a pulse detonation rocket engine with a different configuration was invented.A central cone instead of Shchelkin spiral was used in this engine.Reactants could be injected into the engine both through the engine head and the central cone.With kerosene used as fuel,oxygen as oxidizer and nitrogen as purge gas,fully developed detonation waves were generated in this engine,which could operate steadily on multi-cycle mode.The result also indicates that this engine could greatly shorten the DDT (deflagration to detonation transition) run-up distance,and the DDT run-up distance is approximately five times of the inner diameter of detonation tube.Compared with the approach of installing Shchelkin spiral in the detonation tube as DDT enhancement device,the DDT run-up distance of this engine was shortened by 57.5%.
- liquid fuel /
- pulse detonation rocket engine /
- central cone /
- two-stage filling /

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参考文献(12)

[1]	Bussing T,Pappas G.An introduction to pulse detonation engines .AIAA-1994-0263,1994.
[2]	Kailasanath K.Recent developments in the research on pulse detonation engines[J].AIAA Journal,2003,41(2):145-159.
[3]	Heiser W H,Pratt D T.Thermodynamics cycle analysis of pulse detonation engines[J].Journal of Propulsion and Power,2002,18(1):68-76.
[4]	严传俊,范玮.脉冲爆震发动机原理及关键技术[M].西安:西北工业大学出版社,2005.
[5]	LI Qiang,FAN Wei,YAN Chuanjuan,et al.Experimental investigation of performance of pulse detonation rocket engine model[J].Chinese Journal of Aeronautics,2007,20(1):9-14.
[6]	FAN Wei,YAN Chuanjuan,HUANG Xiqiao,et al.Experimental investigation on two-phase pulse detonation engine[J].Combustion and Flame,2003,133(4):441-450.
[7]	Lee S Y,Watts J,Saretto S,et al.Deflagration to detonation transition process by turbulence-generating obstacles in pulse detonation engines[J].Journal of Propulsion and Power,2004,20(6):1026-1036.
[8]	胡承启,范玮,严传俊,等.当量比对脉冲爆震火箭发动机性能影响的实验研究[J].机械科学与技术,2007,26(6):751-753. HU Chenqi,FAN Wei,YAN Chuanjun,et al.Experimental study of the effect of equivalence ratio on performance of pulse detonation rocket engine[J].Mechanical Science and Technology for Aerospace Engineering,2007,26(6):751-753.(in Chinese)
[9]	李强,范玮,严传俊,等.脉冲爆震火箭发动机模型实验研究[J].西北工业大学学报,2005,23(5):549-552. LI Qiang,FAN Wei,YAN Chuanjun,et al.Investigation practicability of using liquid fuel kerosene in pulse detonation rocket engine model[J].Journal of Northwestern Polytechnical University,2005,23(5):549-552.(in Chinese)
[10]	王治武,严传俊,范玮,等.脉冲爆震发动机的点火-起爆性能[J].燃烧科学与技术,2009,15(5):412-416. WANG Zhiwu,YAN Chuanjun,FAN Wei,et al.Ignition-detonation performance of pulse detonation engines[J].Journal of Combustion Science and Technology,2009,15(5):412-416.(in Chinese)
[11]	严宇,范玮,严传俊,等.变截面脉冲爆震火箭发动机实验研究[J].实验流体力学,2009,23(4):7-10. YAN Yu,FAN Wei,YAN Chuanjun,et al.Experimental investigation of the pulse detonation rocket engines with variable cross-section [J].Journal of Experiments in Fluid Mechanics,2009,23(4):7-10.(in Chinese)
[12]	Sorin R,Zitoun R,Desbordes D.Optimization of length and time of transition[J].Shock Waves,2006,15(2):137-145.